National Aeronautics and Space Administration
NASA’s Space Launch System: A Revolutionary Capability for Science
Bill Hill Deputy Associate Administrator Exploration Systems Development Division NASA Headquarters
Stephen Creech Deputy Manager SLS Spacecraft/Payload Integration and Evolution
July 2014 Space Launch System Space Launch
www.nasa.gov/sls www.nasa.gov/sls SLS: An Evolving Capability
Cargo Fairing Launch Abort System 33 ft (10m) Orion, Multi-Purpose Crew Vehicle (MPCV- LMCO) Commonality of Payload Interfaces • Mechanical Interim Cryogenic • Avionics Propulsion Stage (ICPS) • Software (EELV 5m DCSS – Upper Stage & Core Stage Commonality Upper Boeing/ULA) Stage • Same diameter (27.5 ft.) and basic design • Manufacturing facilities, tooling, materials, & processes/practices Core Stage/Avionics • Workforce (Boeing) • Supply chain/industry base • Transportation logistics • Ground systems/launch infrastructure Advanced 5-Segment Solid • Propellants Solid or Rocket Booster Liquid (SRB) (ATK) Commonality of Core Stage (i.e., RP Engines) Boosters Core Stage Engines (RS-25) Commonality of Engines (Aerojet Rocketdyne)
Block 1 Evolutionary Path to Future Capabilities Block 2 Capability Initial Capability, 2017-21 • Minimizes unique configurations 130 metric ton 70 metric ton Payload • Allows incremental development Payload
www.nasa.gov/sls 8562 Space Propulsion 2014_G. Lyles.2 SLS’ Primary Mandate
www.nasa.gov/sls 8335_SLS_JPL.3 Human Spaceflight and Space Science
www.nasa.gov/sls SLS Availability for Space Science
u SLS is on schedule and within budget for to be available for launches beginning in 2017.
u 5-meter payload fairings allow for payload envelopes compatible with current EELVs.
u Cargo-launch variants offer the reliability of a human-mission launch and power in excess of any launch vehicle in history.
www.nasa.gov/sls SLS Development Milestones
www.nasa.gov/sls MSFC_RSA_Update 2014.6 SLS Benefits to Space Science
u Greatest mass lift capability of any launch vehicle in the world. Mars Sample Return Deep Space Telescope u Largest payload fairings of any launch vehicle produce greatest available volume.
u High departure energy availability for missions through the solar system Europa Clipper Solar Probe and beyond.
Uranus Spacecraft Interstellar www.nasa.gov/sls Benefit: SLS Mass Lift Capability
Medium/Intermediate Heavy Super Heavy
u SLS initial
configuration offers 200’ Retired 70 t to LEO.
u Future configurations 100’ offer 105 and 130 t to LEO.
ULA SpaceX ULA NASA NASA NASA NASA u Mass capability Atlas V 551 Falcon 9 Delta IV H Space Shuttle Saturn V 70 t 130 t benefits mean larger 160 1800 140 1600 payloads to any Payload Volume (m 120 1400 destination. 1200 100 1000 80 800 60 600
40 3 Payload MassPayload (mT) 400 ) 20 200 0 0
Mass (mT) Volume (m3) www.nasa.gov/sls Case Study: Mars Sample Return
u Mars Sample Return was identified as a high priority in the “Visions and Voyages” planetary science decadal survey.
u SLS offers single-launch option for Mars Sample Return, versus three launches with EELVs.
u Additional benefits of SLS for Mars Sample Return include reduced mission time, increased sample mass, and reduced mission cost, complexity and risk.
www.nasa.gov/sls Benefit: Unrivaled Payload Volume
u SLS is investigating utilizing existing fairings for early cargo flights, offering payload envelope compatibility with design for current EELVs
u Phase A studies in work for 8.4m and 10 m fairing options
4m x 12m 5m x 14m 5m x 19m 8.4m x 31m 10m x 31m (100 m3) (200 m3) (300 m3) (1200 m3) (1800 m3) 10 www.nasa.gov/sls
Case Study: ATLAST
u Large-aperture spectroscopic telescope was identified as a vital step in the “Enduring Quests, Daring Visions” astrophysics roadmap.
u SLS is uniquely enabling for largest- diameter telescopes due to fairing- width requirements.
u Additional benefits of SLS for ATLAST include opportunities for human assembly and/or servicing at deep space destinations.
www.nasa.gov/sls Benefit: High Departure Energy
u Even the Initial configuration of SLS offers orders of magnitude greater payload-to- destination energy compared to existing launch vehicles; future configurations improve C3 performance even further.
u Departure energy offers faster transit time to destination, including 4-7 year reduction to Saturn or 6 years to Uranus.
u Higher departure energy offers more launch opportunities.
u Trade space exists between departure energy and mass capability; a Jovian mission could see 3-year transit reduction or 13 t mass increase.
12 www.nasa.gov/sls SLS Evolved Performance
Saturn Saturn/ Lunar Mars Jupiter/Europa via JGA Uranus Direct 70.00# SLS#Block#1#+#Orion#+#iCPS# SLS#Block#1#+#5.0m#Fairing#+#iCPS# 60.00# SLS#Block#1B#+#5.0m#Fairing#+#EUS#(TBD)# SLS#Block#1B#+#8.4m#Fairing#+#EUS# SLS#Block#2B#+#8.4m#Fairing#+#EUS#+#Advanced#Boosters#(min+max)# 50.00# SLS#Block#2B#+#10m#Fairing#+#EUS#+#Advanced#Boosters#(TBD)# Delta#IV#Heavy#+#2007#PPG# Atlas#V#551#NASA#LSP# 40.00# Europa#Class#Mission# 5m#x#19m# 8.4m#x#19m# 10m#x#31m# (300#m3)# (620#m3)# (1800#m3)# # # 30.00# # EM-1
20.00# Net$Payload$System$Mass$(mt)$ 10.00# Europa
0.00# +10# 0# 10# 20# 30# 40# 50# 60# 70# 80# 90# 100# 110# 120# 130# 140# 150# Characteris6c$Energy,$C3$(km2/s2)$
www.nasa.gov/sls Case Study: Europa Clipper
u Europa exploration was identified as a high priority in the “Visions and Voyages” planetary science decadal survey.
u SLS can provide direct injection to Jupiter, eliminating several years of planetary gravity assists to reduce flight time to Europa from 6.3 years to 2.7.
u Additional benefits of SLS for Europa Clipper include reduced operational costs, reduced mission risk, and greater mass margin.
www.nasa.gov/sls Outer Planet EELV Trajectories
Galileo Trajectory To Jupiter Cassini TrajectoryFigure 5.2 CASSINI - PRIMARY to Saturn MISSION CRUISE TRAJECTORY
SATURN ARRIVAL FLYBY (1) FLYBY (2) DEC 8, 1990 DEC 8, 1992 VENUS 1 FLYBY 1 JUL 2004 APR-MAY 1998
LAUNCH OCT 18, 1989 VENUS VENUS 2 FLYBY JUN 1999
FLYBY FEB 10, MANEUVER* 1990 MAR-APR 1998
IDA MANEUVER AUG 28, 1993 JAN 1999
JUPITER JAN 1, 1994 COMPLETE PRIMARY GASPRA MISSION DATA RETURN OCT 29, 1991 DEC 7, 1997
COMET S-L IMPACT OBSERVATIONS 7/94 JUPITER FLYBY E11 JUPITER 30 DEC 2000 MAGNETOTAIL C10 LAUNCH PROBE RELEASE EXPLORATION OCT-NOV 1997 7/13/95 C9 G8 ORBITER DEFLECTION G7 EARTH FLYBY 7/20/95 E6 AUG 1999 5 E4 C3 PERIHELIA PJR G2 MAR 1998 0.68 AU G1 GANYMEDE, CALLISTO, JUN 1999 0.72 AU EUROPA, ENCOUNTERS Cruise: 6.1 yr. JUPITER ARRIVAL IN ORBIT * this maneuver is only needed for launch dates after Oct. 25th AND Io ENCOUNTER Cruise: 6.7 yr. DEC 7, 1995 5-3
19 JUNO Trajectory To Jupiter Atlas V Clipper Trajectory
Cruise: 4.9 yr. Cruise: 6.4 yr. www.nasa.gov/sls Europa Trajectory Comparison
Atlas V 551: VEEGA SLS: Direct
VGA (5/14/22) JOI (4/4/28) EGA-1 (10/24/23)
EGA-2 Launch (10/24/25) (11/21/21)
Jupiter’s Orbit Launch (6/5/22) DSM (7/10/22)
REDUCES TRANSIT TIME TO EUROPA FROM 6.5 TO 2.7 YEARS
16 www.nasa.gov/sls SLS Secondary Payload Capability
u SLS is providing accommodations for secondary payloads on EM-1 and subsequent launches
u Secondary payloads will be accommodated in the Orion- MPCV Spacecraft Adapter (MSA) on EM-1
u 6U equivalent volume/mass is the current standard; 12U volume can be accommodated • 12U mass still being evaluated • Additional mounting locations are being evaluated
u SLS provides secondary payload science opportunities beyond EELVs capabilities (Lunar and beyond)
www.nasa.gov/sls Possible Next Step: ARRM
u The Asteroid Redirect Robotic Mission is an early step on NASA’s Path to Mars.
u SLS offers reduced transit time, providing earlier redirection of target and/ or greater launch opportunities.
u Additional benefits of SLS for ARRM offer the potential for redirecting a larger object and for enabling a wider variety of targets.
u SLS could launch an ARRM spacecraft as early as 2019.
u SLS provides capability for human exploration missions. • 70 t configuration enables EM-1 and EM-2 flight tests. • Evolved configurations enable missions including humans to Mars.
u SLS offers unrivaled benefits for a variety of missions. • 70 t provides greater mass lift than any contemporary launch vehicle; 130 t offers greater lift than any launch vehicle, ever. • With 8.4m and 10m fairings, SLS will over greater volume lift capability than any other vehicle. • Initial ICPS configuration and future evolution will offer highest- ever C3.
u SLS is currently on schedule for first launch in December 2017. • Preliminary design completed in July 2013; SLS is now in implementation. • Manufacture and testing are currently underway. • Hardware now exists representing all SLS elements. 19 www.nasa.gov/sls Somewhere, something incredible is waiting to be known. — Carl Sagan
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